METHOD FOR MANUFACTURING AND ASSEMBLY OF A THRUST REVERSER CASCADE
A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.
This disclosure relates to a cascade for a thrust reverser for a jet engine and more particularly to a method of manufacturing and assembling of the cascade.
BACKGROUNDThrust reversers are devices used to turn jet engine exhaust to a direction with a sufficient forward component to create reverse thrust to enable aerodynamic breaking during an airplane landing maneuver. A cascade is a component of the thrust reverser assembly mounted to a nacelle of a jet engine. A blocker door of the thrust reverser assembly directs exhaust air flow to and through the cascade and the cascade configuration further directs the exhaust air flow which exits the cascade.
A cascade typically includes surfaces which will selectively direct the exhaust flow in forward and side directions. The direction of the exhaust air flow is tailored by the direction of the surfaces of vanes and strong backs within the cascade. Vane surfaces selectively direct the exhaust air flow in a forward direction and strong backs selectively direct the exhaust air flow in a side-turning direction. Cascades, as a result of having surfaces which direct exhaust air flow in varied directions, have a complex shape. The complex shape results in considerable labor, cost and turnaround time for production.
Cascades have been made conventionally with composite material by way of hand layups. This fabrication methodology is labor intensive and results in a high cost. Other methods of manufacturing cascades has included compression mold thermoplastic manufacturing processes which is less labor intensive but which has complex four sided mold designs which result in requiring complicated mold shapes. With the cascade having four sided structures, this configuration has necessitated complicated installation, removal and tracking procedures of these molded pieces which add cost penalties with respect to labor efforts required and the length of time of the process.
Although the above compression mold thermoplastic manufacturing process can be streamlined to reduce manufacturing cost, the streamlining requires simplification of the aerodynamic lines of the cascade geometry which directs the exhaust air flow. As a result of simplification of the aerodynamic lines of the cascade geometry, the reverse thruster aerodynamic performance is penalized. To compensate for the reduced aerodynamic performance relatively larger cascades are required. These cascades are typically required to be longer. This increase in size further contributes to increased weight and installation challenges such as, the aerolines of the fan outer wall and external nacelle, longer actuators etc. Any change in aerolines requires re-certification costs and further additional testing costs.
There is a need to manufacture cascades which perform the needed function of directing exhaust air flow from the jet engine. The cascade will need to direct the exhaust air flow in various directions so as to avoid imparting wear onto different parts of the aircraft and to direct flow in a forward direction of the aircraft to slow down the speed of the aircraft after the aircraft has touched down on the airstrip in a landing maneuver. The manufacturing of cascades also needs to be less labor intensive and less expensive without compromising the needed aerodynamic performance of the cascade which would otherwise place increased challenges on installation and impose cost penalties associated with re-certification.
SUMMARYAn example of a method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly also includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.
An example of a method of assembling a cascade for a thrust reverser for a jet engine includes the steps of placing a strip assembly into a first position wherein the strip assembly includes a strong back member having a length. The strip assembly further includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the first vane members are spaced apart from one another along the length of the strong back member. The method further includes placing a second strip assembly into a second position wherein the second strip assembly includes a second strong back member which includes a length. The second strip assembly further includes a plurality of third vane members which extend from a second side of the second strong back member in a third direction nonparallel relative to the length of the second strong back member wherein the plurality of third vane members are spaced apart from one another along the length of the second strong back member. With the strip assembly in the first position and the second strip assembly in the second position, one of the plurality of first vane members adjoins one of the plurality of third vane members.
An example of a thrust reverser cascade includes a strip assembly which includes a strong back member which further includes a plurality of first vane members which extend from a first side of the strong back member. Also included is a second strip assembly which includes a second strong back member which includes a plurality of third vane members which extend from a second side of the second strong back member. The strip assembly is secured at opposing end portions of the strip assembly to a nacelle and the second strip assembly is secured at opposing end portions of the second strip assembly to the nacelle. With each of the strip assembly and the second strip assembly secured to the nacelle, a distal end of one of the first vane members adjoins a distal end of one of the third vane members.
An example of a method for manufacturing a cascade for a thrust reverser for a jet engine which includes forming a vane strip assembly, wherein the vane strip assembly includes a vane member comprising a length; and a plurality of first strong back members which extend from a first side of the vane member in a first direction nonparallel relative to the length of the vane member wherein the plurality of the first strong back members are spaced apart from one another along the length of the vane member.
An example of a method for assembling a cascade for a thrust reverser for a jet engine which includes the steps of placing a vane strip assembly into a first position wherein the vane strip assembly includes: a vane member comprising a length; and a plurality of first strong back members which extend from a first side of the vane member in a first direction nonparallel relative to the length of the vane member wherein the first strong back members are spaced apart from one another along the length of the vane member. The method further includes the step of placing a second vane strip assembly into a second position wherein the second vane strip assembly which includes: a second vane member comprising a length; and a plurality of third strong back members which extend from a second side of the second vane member in a third direction nonparallel relative to the length of the second vane member. The plurality of third strong back members are spaced apart from one another along the length of the second vane member; and with the strip assembly in the first position and the second vane strip assembly in the second position, one of the plurality of first strong back members adjoins one of the plurality of third strong back members.
An example includes a reverse thruster cascade which includes a vane strip assembly which includes a vane member comprising a plurality of first strong back members which extend from a first side of the vane member. The reverse thruster cascade further includes a second vane strip assembly including a second vane member comprising a plurality of third strong back members which extend from a second side of the second vane member. The vane strip assembly is secured at opposing end portions of the vane strip assembly to a nacelle. The second vane strip assembly is secured at opposing end portions of the second vane strip assembly to the nacelle such that with each of the vane strip assembly and the second vane assembly secured to the nacelle a distal end of one of the plurality of the first strong back members adjoins a distal end of one of the plurality of the third strong back members.
The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments further details of which can be seen with reference to the following description and drawings.
As discussed above, thrust reversers are devices used to turn jet engine exhaust to a direction with a sufficient forward component to create reverse thrust to enable aerodynamic breaking during an airplane landing maneuver. Cascade 10, as seen in
Cascades 10, as previously mentioned, include surfaces which will selectively direct the exhaust air flow in a forward and side directions as needed. The direction of the air flow is tailored by the direction of the surfaces of vanes 18, as seen in
A method for manufacturing and assembling cascade 10 for a thrust reverser will be discussed herein, wherein the manufacturing and assembly will be streamlined so as to require less labor, cost and production time. Furthermore, the methodology for manufacturing and assembling of cascade 10 in the present disclosure will be performed without compromising the needed aerodynamic performance of cascade 10 which would otherwise lead to yet additional installation and re-certification costs.
There are a variety of methodologies that can be employed to manufacture and assemble cascade 10 which includes methods for forming strip assembly 19, as seen in
In referring to
Plurality of first vane members 30 includes curvilinear surface 36, as seen in
Method 26 further includes plurality of second vane members 48, as seen in
As seen in
As seen in
At least one second vane members 48 is similar in construction in this example to first vane members 30, as seen in
Step 28 further includes strong back member 22 including first side surface 32 which extends along length L of strong back member 22 and extends transverse to length L of strong back member 22. Also included is second side surface 50 of strong back member 22 opposing first side 32, wherein second side surface 50 also extends along length L of strong back member 22 and extends transverse to length L of strong back member 22, as seen in
Second side 50 opposing first side 32 of strong back member 22 extends along length L of strong back member 22 and extends transverse to length L of strong back member 22. Second side 50 of strong back member 22 has top portion 64 such that, with strip assembly 19 positioned on nacelle 12 of jet engine 14, top portion 64 of second side surface 50 extends in fifth direction 66 relative to radial direction 62 which extends from central axis 46 of jet engine 14 and aligned with strong back member 22 positioned closer to central axis 46 of jet engine 14 than top portion 64 of second side 50 of strong back member 22. Fifth direction 66 extends relative to radial direction 62 within an angular range including extending parallel with radial direction 62 and up to and including being angularly displaced sixty degrees from radial direction 62, as seen for example as angle C in
In referring to
In referring to
A first example of the various configurations that can be employed to distal end 76 and distal end 78 includes distal end 76 of first vane member 30 extends along first plane 80, as seen in
Method 68 of assembling of cascade 10 further includes one of the plurality of first vane members 30, as seen in
Method 68 further includes strong back member 22 including front portion 40 which extends from first side 32 of strong back member 22. Second strong back member 22′ includes a second front portion 40′ which extends from second side 50′ of second strong back member 22′ as seen for example in
In referring to
In one example, distal end 92 of the front portion 40 of strong back member 22 extends in a first plane 96 (generally represented by arrow 96) and distal end 94 of second front portion 40′ of second strong back member 22′ extends in second plane 98 (generally represented by arrow 98) wherein first plane 96 and second plane 98 extend in the same direction. In a second example, one of distal end 92 of front portion 40 of strong back member 22 or distal end 94 of second front portion 40′ of second strong back member 22′ defines an angularly shaped configuration 100. In the example shown in
Vane assemblies 74 which include for example first vane member 30 and third vane member 48′ in cascade 10 and front portions including front portion 40 and second front portion 40′ can be secured to secured to one another in the assembling of cascade 10. A variety of securements can be used employing methodologies such as patch bonding, glue bonding, welding or applying rivets or other types of fasteners. In other instances, as will be described below, cascade 10 can be assembled onto nacelle 12 with securement of each strip assembly at the opposing ends of the strip assemblies to nacelle 12.
Cascade 10 as described above includes strip assembly 19, which further includes strong back member 22 having plurality of first vane members 30 which extend from first side 32 of strong back member 22 as seen in
At least one of plurality of first vane members 30 and at least one of plurality of third vane members 48′ include curvilinear surface 36 and 54′ respectively, as seen in
As discussed earlier, at least one of the plurality of first vane members 30 and at least one of the plurality of third vane members 48′, as seen in
Cascade 10 includes strong back member 22, as seen in
Cascade 10 further includes at least one of the plurality of the first vane members 30 include a distal end 76 relative to strong back member 22. Cascade 10 further includes at least one of the plurality of third vane members 48′ which includes distal end 78 relative to second strong back member 22. Distal end 76 of first vane members 30 adjoin distal end 78 of third vane members 48′ in one of the several configurations described herein. In one configuration example, distal end 76 of at least one of the first vane members 30 extends along in first plane 96 and distal end 78 of one of the third vane members 48′extends along in second plane 98, wherein first plane 96 and second plane 98 extend in the same direction. In a second configuration example, distal end 76 of one of the plurality of first vane members 30 or distal end 78 of one of the plurality of third vane members 48′ defines an angularly shaped configuration 84 and distal end 78 of the other of one of the plurality of first vane members 30 or of one of the plurality of third vane members 48′ defines complementary shape 86 relative to angularly shaped configuration 84. As shown in an example in
Now in referring to
The step of forming 114 further includes vane member 118, as seen in
Step 114 of forming further includes a plurality of second strong back members 132, as seen in
Step 114 of forming of method 112 further includes first strong back member 122 of
In further discussing first strong back member 122 in terms of being similar structure of strong back member 22 in
In referring to
Method 138 of
With adjoining vane strip assembly 116 and second vane strip assembly 116′ distal ends of first strong back members 122 and third strong back members 132′ adjoin. Method 138 of assembling includes a distal end 148 of one of the plurality of first strong back members 122, relative to first side 124 of vane member 118, and distal end 150 of the one of the plurality of third strong back members 132′, relative to second side 134′ of the second vane member 118′, adjoin one another in one of the following discussed configurations. In one configuration example, distal end 148 of one of the first strong back members 122, as seen in
In another example of a configuration of distal ends, distal end 156 of one of plurality of strong back members 122 or distal end 158 of one of the plurality of third strong back members 132′defines an angularly shaped configuration 160. In the example shown in
In yet another example of a configuration, as shown in
As seen in
As discussed earlier, at least one of vane member 118 and second vane member 118′include a curvilinear surface 128 wherein curvilinear surface 128 forms recess 130 facing forward position 20. This is seen in
One of the plurality of first strong back members 122 and one of the plurality of third strong back members 132′, as seen in
First strong back member 122 includes, as earlier discussed as being similar in structure as strong back member 22 and shown in
Second side 50, as seen in
As discussed earlier and shown in
In another example of a configuration of distal ends, distal end 156 of one of plurality of strong back members 122 or distal end 158 of one of the plurality of third strong back members 132′ defines an angularly shaped configuration 160. In the example shown in
In yet another example of a configuration, as shown in
Reverse thruster cascade 10′ as shown in
While various embodiments have been described above, this disclosure is not intended to be limited thereto. Variations can be made to the disclosed embodiments that are still within the scope of the appended claims.
Claims
1. Method for manufacturing a cascade for a thrust reverser for a jet engine, comprising:
- forming a strip assembly, wherein the strip assembly comprises: a strong back member comprising a length; and a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of the strong back member wherein the plurality of first vane members are spaced apart from one another along the length of the strong back member.
2. The method of claim 1 wherein the step of forming further includes at least one of the plurality of first vane members comprises a curvilinear surface wherein the curvilinear surface forms a recess facing a forward direction.
3. The method of claim 2 wherein the step of forming further includes a top portion of the curvilinear surface extends in a second direction nonparallel relative to a central axis of the jet engine such that, with the strip assembly positioned on a nacelle of the jet engine, the second direction forms an angle relative to the central axis of the jet engine in a range including thirty degrees up to and including ninety degrees.
4. The method of claim 1 wherein the step forming further includes a plurality of second vane members which extend from a second side of the strong back member, opposing the first side of the strong back member, in a third direction nonparallel relative to the length of the strong back member wherein the plurality of second vane members are spaced apart from one another along the length of the strong back member.
5. The method of claim 4 wherein the step of forming further includes one first vane member of the plurality of first vane members and one second vane member of the plurality of second vane members extend in alignment with one another.
6. The method of claim 5 wherein the step of forming further includes each of the plurality of the first vane members is positioned to extend from the strong back member in alignment with one second vane member of the plurality of the second vane members.
7. The method of claim 4 wherein the step of forming further includes a length of one of the plurality of first vane members and a length of the one of the plurality of second vane members are positioned in angular relationship to one another.
8. The method of claim 4 wherein the step of forming further includes at least one of the plurality of the second vane members comprises a curvilinear surface wherein the curvilinear surface forms a recess which faces a front portion of the strip assembly.
9. The method of claim 8 wherein the step of forming further includes a top portion of the curvilinear surface extends in a second direction nonparallel relative to a central axis of the jet engine such that, with the strip assembly positioned on a nacelle of the jet engine, the second direction forms an angle relative to a central axis of the jet engine in a range including thirty degrees up to and including ninety degrees.
10. The method of claim 1 wherein the step of forming further includes the strong back member comprising a first side and a second side opposing the first side, wherein:
- the first side extends along the length of the strong back member and extends transverse to the length of the strong back member;
- the first side of the strong back member has a top portion such that, with the strip assembly positioned on the nacelle of the jet engine, the top portion of the first side extends in a fourth direction relative to a radial direction, which extends from the central axis of the jet engine and aligned with the strong back member positioned closer to the central axis of the jet engine than the top portion of the first side of the strong back member, wherein the fourth direction extends relative to the radial direction within an angular range including extending parallel with the radial direction and up to and including being angularly displaced sixty degrees from the radial direction;
- the second side opposing the first side extends along the length of the strong back member and extends transverse to the length of the strong back member; and
- the second side of the strong back member has a top portion such that, with the strip assembly positioned on the nacelle of the jet engine, the top portion of the second side extends in a fifth direction relative to the radial direction, which extends from the central axis of the jet engine and aligned with the strong back member positioned closer to the central axis of the jet engine than the top portion of the second side of the strong back member, wherein the fifth direction extends relative to the radial direction within an angular range including extending parallel with the radial direction and up to and including being angularly displaced sixty degrees from the radial direction.
11. A method of assembling a cascade for a thrust reverser for a jet engine, comprising the steps of:
- placing a strip assembly into a first position wherein the strip assembly comprises: a strong back member comprising a length; and a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of the strong back member wherein the first vane members are spaced apart from one another along the length of the strong back member; and
- placing a second strip assembly into a second position wherein the second strip assembly comprises: a second strong back member comprising a length; and a plurality of third vane members which extend from a second side of the second strong back member in a third direction nonparallel relative to the length of the second strong back member wherein: the plurality of third vane members are spaced apart from one another along the length of the second strong back member; and with the strip assembly in the first position and the second strip assembly in the second position, one of the plurality of first vane members adjoins one of the plurality of third vane members.
12. The method of assembling of claim 11 further includes a distal end of the one of the plurality of first vane members relative to the first side of the strong back member and a distal end of the one of the plurality of third vane members relative to the second side of the second strong back member, adjoin one another in one of the following configurations:
- the distal end of the one of the first vane members extend along in a first plane and the distal end of the one of the third vane members extend along in a second plane wherein the first plane and the second plane extend in the same direction; or
- the distal end of the one of the plurality of first vane members or a distal end of the one of the plurality of third vane members defines an angularly shaped configuration and the distal end of the other of the one of the plurality of first vane members or of the one of the plurality of third vane members defines a complementary shape relative to the angularly shaped configuration; or
- the distal end of the one of the plurality of first vane members or a distal end of the one of the plurality of third vane members defines a protrusion and the distal end of the other of the one of the plurality of first vane members or of the one of the plurality of the third vane members defines a notch wherein the protrusion and the notch are complementary in shape to one another interlocking the one of the plurality of the first vane member and the one of the plurality of the third vane member.
13. The method of assembling of claim 11 further includes the one of the plurality of first vane members extends away from the first side of the strong back member toward the second strong back member and the one of the plurality of third vane members extends away from the second side of the second strong back member toward the strong back member positioning the one of the plurality of the first vane members and the one of the plurality of third vane members in angular relationship to one another.
14. The method of assembling of claim 11, wherein:
- the strong back member includes a front portion which extends from the first side of the strong back member; and
- the second strong back member includes a second front portion which extends from the second side of the second strong back member and with the strip assembly in the first position and the second strip assembly in the second position the front portion of the strong back member adjoins the second front portion of the second strong back member, wherein a distal end of the front portion of the strong back member and a distal end of the second front portion of the second strong back member adjoin one another in one of the following configurations: the distal end of the front portion of the strong back member extends in a first plane and the distal end of the second front portion of the second strong back member extends in a second plane wherein the first plane and the second plane extend in the same direction; or one of the distal end of the front portion of the strong back member or the distal end of the second front portion of the second strong back member defines an angularly shaped configuration and the other of the distal end of the front portion of the strong back member or the distal end of the second front portion of the second strong back member defines a complementary shape to the angularly shaped configuration; or the distal end of the front portion of one of the front portion of the strong back member or the distal end of the second front portion of the second strong member defines a protrusion and the other of the distal end of the front portion of the strong back member or the second front portion of the second strong back member defines a notch wherein the protrusion and the notch are complementary in shape to one another interlocking the front portion of the strong back member and the second front portion of the second strong back member.
15. A reverse thruster cascade, comprising:
- a strip assembly comprising a strong back member comprising a plurality of first vane members which extend from a first side of the strong back member;
- a second strip assembly comprising a second strong back member comprising a plurality of third vane members which extend from a second side of the second strong back member; wherein:
- the strip assembly is secured at opposing end portions of the strip assembly to a nacelle; and
- the second strip assembly is secured at opposing end portions of the second strip assembly to the nacelle such that with each of the strip assembly and the second strip assembly secured to the nacelle a distal end of one of the plurality of the first vane members adjoins a distal end of one of the plurality of the third vane members.
16. The reverse thruster cascade of claim 15 wherein:
- the one of the plurality of first vane members and the one of the plurality of third vane members comprise a curvilinear surface;
- the curvilinear surface forms a recess facing a forward position; and
- a top portion of the curvilinear surface extends in a second direction nonparallel relative to a central axis of the jet engine such that, with the strip assembly positioned on a nacelle of the jet engine, the second direction forms an angle relative to the central axis of the jet engine in a range including thirty degrees up to and including ninety degrees.
17. The reverse thruster cascade of claim 15 wherein the one of the plurality of first vane members and the one of the plurality of third vane members extend in alignment with one another forming a vane assembly between the strip assembly and the second strip assembly.
18. The reverse thruster cascade of claim 15 wherein a length of the one of the plurality of first vane members and a length of the one of the plurality of third vane members are positioned in angular relationship to one another forming a second vane assembly between the strip assembly and the second strip assembly.
19. The reverse thruster cascade of claim 15 wherein:
- the strong back member comprises a first side and a second side opposing the first side;
- the first side extends along the length of the strong back member and extends transverse to the length of the strong back member and the second side extends along the length of the strong back member and extends transverse to the length of the strong back member;
- the first side of the strong back member has a top portion such that with the strip assembly positioned on the nacelle of the jet engine, the top portion of the first side extends in a fourth direction relative to a radial direction, which extends from the central axis of the jet engine and aligned with the strong back member positioned closer to the central axis of the jet engine than the top portion of the first side of the strong back member;
- the fourth direction is angularly positioned with respect to the radial direction in a directional range which includes parallel to the radial direction to and including up to sixty degrees angularly displaced from parallel with the radial direction;
- the second side of the strong back member has a top portion such that with the strip assembly positioned on the nacelle of the jet engine the top portion of the second side extends in a fifth direction relative to the radial direction which extends from the central axis of the jet engine and aligned with the strong back member positioned closer to the central axis of the jet engine than the top portion of the second side of the strong back member; and
- the fifth direction is angularly positioned with respect to the radial direction in a directional range which includes parallel to the radial direction to and including up to sixty degrees angularly displaced from parallel with the radial direction.
20. The reverse thruster cascade of claim 15 further comprising:
- the distal end of one of the plurality of the first vane members and the distal end of one of the plurality of the third vane members adjoin one another in one of the following configurations: the distal end of the one of the first vane members extend along in a first plane and the distal end of the one of the third vane members extend along in a second plane wherein the first plane and the second plane extend in the same direction; or the distal end of the one of the plurality of first vane members or a distal end of the one of the plurality of third vane members defines an angularly shaped configuration and the distal end of the other of the one of the plurality of first vane members or of the one of the plurality of third vane members defines a complementary shape relative to the angularly shaped configuration; or the distal end of the one of the plurality of first vane members or a distal end of the one of the plurality of third vane members defines a protrusion and the distal end of the other of the one of the plurality of first vane members or of the one of the plurality of the third vane members defines a notch wherein the protrusion and the notch are complementary in shape to one another interlocking the one of the plurality of the first vane members and the one of the plurality of the third vane members.
21. A method for manufacturing a cascade for a thrust reverser for a jet engine, comprising:
- forming a vane strip assembly, wherein the vane strip assembly comprises: a vane member comprising a length; and a plurality of first strong back members which extend from a first side of the vane member in a first direction nonparallel relative to the length of the vane member wherein the plurality of the first strong back members are spaced apart from one another along the length of the vane member.
22. The method of claim 21 wherein the step of forming further includes the vane member comprises a curvilinear surface wherein the curvilinear surface forms a recess facing a forward direction.
23. The method of claim 22 wherein the step of forming further includes a top portion of the curvilinear surface extends in a second direction nonparallel relative to a central axis of the jet engine such that, with the vane strip assembly positioned on a nacelle of the jet engine, the second direction forms an angle relative to the central axis of the jet engine in a range including thirty degrees up to and including ninety degrees.
24. The method of claim 21 wherein the step forming further includes a plurality of second strong back members which extend from a second side of the vane member, opposing the first side of the vane member, in a third direction nonparallel relative to the length of the vane member wherein the plurality of second strong back members are spaced apart from one another along the length of the vane member.
25. The method of claim 24 wherein the step of forming further includes one first strong back member of the plurality of first strong back members and one second strong back member of the plurality of second strong back members extend in alignment with one another.
26. The method of claim 25 wherein the step of forming further includes each of the plurality of the first strong back members is positioned to extend from the vane member in alignment with one second strong back member of the plurality of the second strong back members.
27. The method of claim 21 wherein the step of forming further includes the first strong back member comprising a first side and a second side opposing the first side, wherein:
- the first side of the first strong back member has a top portion such that, with the vane strip assembly positioned on the nacelle of the jet engine, the top portion of the first side extends in a fourth direction relative to a radial direction, which extends from the central axis of the jet engine and aligned with the strong back member positioned closer to the central axis of the jet engine than the top portion of the first side of the first strong back member, wherein the fourth direction extends relative to the radial direction within an angular range including extending parallel with the radial direction and up to and including being angularly displaced sixty degrees from the radial direction; and
- the second side of the first strong back member has a top portion such that, with the vane strip assembly positioned on the nacelle of the jet engine, the top portion of the second side extends in a fifth direction relative to the radial direction, which extends from the central axis of the jet engine and aligned with the strong back member positioned closer to the central axis of the jet engine than the top portion of the second side of the first strong back member, wherein the fifth direction extends relative to the radial direction within an angular range including extending parallel with the radial direction and up to and including being angularly displaced sixty degrees from the radial direction.
28. A method for assembling a cascade for a thrust reverser for a jet engine, comprising the steps of:
- placing a vane strip assembly into a first position wherein the vane strip assembly comprises:
- a vane member comprising a length; and
- a plurality of first strong back members which extend from a first side of the vane member in a first direction nonparallel relative to the length of the vane member wherein the first strong back members are spaced apart from one another along the length of the vane member; and
- placing a second vane strip assembly into a second position wherein the second vane strip assembly comprises: a second vane member comprising a length; and a plurality of third strong back members which extend from a second side of the second vane member in a third direction nonparallel relative to the length of the second vane member, wherein: the plurality of third strong back members are spaced apart from one another along the length of the second vane member; and with the strip assembly in the first position and the second vane strip assembly in the second position, one of the plurality of first strong back members adjoins one of the plurality of third strong back members.
29. The method of assembling of claim 28 further includes a distal end of the one of the plurality of first strong back members relative to the first side of the vane member and a distal end of the one of the plurality of third strong back members relative to the second side of the second vane member, adjoin one another in one of the following configurations:
- the distal end of the one of the first strong back members extend along in a first plane and the distal end of the one of the third strong back members extend along in a second plane wherein the first plane and the second plane extend in the same direction; or
- the distal end of the one of the plurality of strong back members or a distal end of the one of the plurality of third strong back members defines an angularly shaped configuration and the distal end of the other of the one of the plurality of first strong back members or of the one of the plurality of third strong back members defines a complementary shape relative to the angularly shaped configuration; or
- the distal end of the one of the plurality of first strong back members or a distal end of the one of the plurality of third strong back members defines a protrusion and the distal end of the other of the one of the plurality of first strong back members or of the one of the plurality of the third strong back members defines a notch wherein the protrusion and the notch are complementary in shape to one another interlocking the one of the plurality of the first strong back member and the one of the plurality of the third strong back member.
30. A reverse thruster cascade, comprising:
- a vane strip assembly comprising a vane member comprising a plurality of first strong back members which extend from a first side of the vane member;
- a second vane strip assembly comprising a second vane member comprising a plurality of third strong back members which extend from a second side of the second vane member; wherein: the vane strip assembly is secured at opposing end portions of the vane strip assembly to a nacelle; and the second vane strip assembly is secured at opposing end portions of the second vane strip assembly to the nacelle such that with each of the vane strip assembly and the second vane assembly secured to the nacelle a distal end of one of the plurality of the first strong back members adjoins a distal end of one of the plurality of the third strong back members.
31. The reverse thruster cascade of claim 30 wherein:
- at least one of the vane member and the second vane member comprise a curvilinear surface;
- the curvilinear surface forms a recess facing a forward position; and
- a top portion of the curvilinear surface extends in a second direction nonparallel relative to a central axis of the jet engine such that, with the vane strip assembly positioned on a nacelle of the jet engine, the second direction forms an angle relative to the central axis of the jet engine in a range including thirty degrees up to and including ninety degrees.
32. The reverse thruster cascade of claim 30 wherein the one of the plurality of first strong back members and the one of the plurality of third vane members extend in alignment with one another forming a strong back assembly between the vane strip assembly and the second vane strip assembly.
33. The reverse thruster cascade of claim 30 wherein:
- first strong back member comprises a first side and a second side opposing the first side;
- the first side of the first strong back member has a top portion such that with the vane strip assembly positioned on the nacelle of the jet engine, the top portion of the first side extends in a fourth direction relative to a radial direction, which extends from the central axis of the jet engine and aligned with the first strong back member positioned closer to the central axis of the jet engine than the top portion of the first side of the first strong back member;
- the fourth direction is angularly positioned with respect to the radial direction in an angular range which includes parallel to the radial direction to and including up to sixty degrees angularly displaced from parallel with the radial direction;
- the second side of the first strong back member has a top portion such that with the vane strip assembly positioned on the nacelle of the jet engine the top portion of the second side extends in a fifth direction relative to the radial direction which extends from the central axis of the jet engine and aligned with the strong back member positioned closer to the central axis of the jet engine than the top portion of the second side of the first strong back member; and
- the fifth direction is angularly positioned with respect to the radial direction in an angular range which includes parallel to the radial direction to and including up to sixty degrees angularly displaced from parallel with the radial direction.
34. The reverse thruster cascade of claim 30 further comprising:
- the distal end of one of the plurality of the first strong back members and the distal end of one of the plurality of the third strong back members adjoin one another in one of the following configurations: the distal end of the one of the plurality of the first strong back members extend along in a first plane and the distal end of the one of the plurality of the third strong back members extend along in a second plane wherein the first plane and the second plane extend in the same direction; or the distal end of the one of the plurality of first strong back members or a distal end of the one of the plurality of third vane members defines an angularly shaped configuration and the distal end of the other of the one of the plurality of first vane members or of the one of the plurality of third vane members defines a complementary shape relative to the angularly shaped configuration; or
- the distal end of the one of the plurality of first strong back members or a distal end of the one of the plurality of third strong back members defines a protrusion and the distal end of the other of the one of the plurality of first strong back members or of the one of the plurality of the third strong back members defines a notch wherein the protrusion and the notch are complementary in shape to one another interlocking the one of the plurality of the first strong back members and the one of the plurality of the third strong back members.
35. A reverse thruster cascade, comprising:
- a vane strip assembly which comprises a vane member comprising a plurality of first strong back members which extend from a first side of the vane member; and
- a second vane strip assembly comprising a second vane member comprising a plurality of third strong back members which extend from a second side of the second vane member, wherein: a vane strip assembly is secured at opposing end portions of the vane strip assembly to a nacelle; and the second vane strip assembly is secured at opposing end portions of the second vane strip assembly to the nacelle such that with each of the vane strip assembly and the second vane strip assembly secured to the nacelle, a distal end of one of the plurality of the first strong back members adjoins a distal end of one of the plurality of the third strong back members.
Type: Application
Filed: May 25, 2017
Publication Date: Nov 29, 2018
Patent Grant number: 10823112
Inventors: Naimishkumar Harpal (Everett, WA), Chen Chuck (Mercer Island, WA), Zachariah VanDeMark (Snohomish, WA), Tunde A. Olaniyan (Bothell, WA), Minkoo Han (Bellevue, WA)
Application Number: 15/605,120